Airworthiness Directive · Amendment 39-19879 · Fuselage
Airbus SAS Airplanes
Superseded. A later AD replaced this one: AD 2023-18-02. Comply with the one in force.
This AD applies to Airbus SAS Model airplanes specified in paragraphs (c)(1) through (4) of this AD, certificated in any category, as identified in European Union Aviation Safety Agency (EASA) AD 2019-0173, dated July 18, 2019 (“EASA AD 2019-0173”).
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, - 113, -114, -115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, - 131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report of cracking found on the frame of the right-hand side sliding window in the flight deck. This AD requires repetitive inspections for cracking of the vertical stiffeners of the left- and right-hand sides of the window frames and corrective actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified in paragraph (h) of this AD: Comply with all required actions and compliance times specified in, and in accordance with, EASA AD 2019-0173.
(1) Where EASA AD 2019-0173 refers to its effective date, this AD requires using the effective date of this AD.
(2) The “Remarks” section of EASA AD 2019-0173 does not apply to this AD.
(3) Paragraph (4) of EASA AD 2019-0173 specifies to report inspection results to Airbus within a certain compliance time. For this AD, report inspection results at the applicable time specified in paragraph (h)(3)(i) or (ii) of this AD.
(i) If the inspection was done on or after the effective date of this AD: Submit the report within 90 days after the inspection.
(ii) If the inspection was done before the effective date of this AD: Submit the report within 90 days after the effective date of this AD.
(4) This AD allows the use of the torque values specified in Section 13 of the Airbus technical adaptations (TAs) identified in paragraphs (h)(4)(i) through (vi) of this AD, when installing a certain eccentric referenced in the applicable Airbus service bulletin, as specified in the applicable TA.
(i) Airbus TA 80662272/007/2019, Issue 1, dated August 29, 2019.
(ii) Airbus TA 80662272/008/2019, Issue 1, dated August 29, 2019.
(iii) Airbus TA 80662272/009/2019, Issue 1, dated August 29, 2019.
(iv) Airbus TA 80662272/010/2019, Issue 1, dated August 29, 2019.
(v) Airbus TA 80696258/006/2019, Issue 1, dated October 29, 2019.
(vi) Airbus TA 80696258/007/2019, Issue 1, dated October 29, 2019.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
